Airbus Operations (s.a.s.)

Benjamin Trarieux

Brice Albert

Stéphane Daure

Cristobal Calatayud

Frédéric Goupil

Harleen Kaur

Julien Bigot

Damien Battistella

A method for manufacturing an aerodynamic structure including a first panel having an aerodynamic face, as well as a second reinforced panel. The method includes a step of stamping the second panel to obtain at least one raised shape which is recessed on the second face, and a step of joining the first and second panels by pressing them against each other outside the at least one raised shape. An aerodynamic shape is obtained using this method.

Method for manufacturing an aerodynamic aircraft structure and aerodynamic aircraft structure thus obtained

A method for installing a screw in at least one through-orifice of a box-type structure, including inserting a body of a first tool into the through-orifice from an external region of the box-type structure, moving the body in an internal region of the box-type structure, towards an end of the box-type structure, securing the screw to the body, the first tool comprising a link connected to the body which remains accessible from the external region during the inserting, moving and securing steps, pulling on the link from the external region until the shank of the screw is positioned in the through-orifice, and separating the body from the screw.

Method for installing a fastener in a through-orifice of a box-type structure open at at least one end, and tooling for carrying out the method

A system includes at least one upper flexible skin intended to be fixed in the extension of an upper plane of the wing, a lower flexible skin intended to be movable in the extension of a lower plane of the wing and fixed along a trailing edge of the control surface, an actuator for generating a displacement of the lower flexible skin with respect to the lower plane. The displacement causes a curvature of the first, upper flexible skin and a curvature of the second, lower flexible skin having a concavity oriented in a same direction. The control surface system makes it possible to reduce the quantity of energy supplied by the actuator.

System of morphing control surface for aircraft wing

A flexible pillar for a variable geometry flight control surface including upper skin and lower skins includes an elongate shape elastic element having an and at least a first end and a second end. The flexible pillar can be disposed between the upper skin and the lower skin so the elastic element can be fixed to the upper skin at the first end of the flexible pillar and fixed to the lower skin at the second end of the flexible pillar. The flexible pillar has a rigidity along the longitudinal axis of the flexible pillar that is greater than a rigidity of the flexible pillar in shear along a transverse axis of the flexible pillar, the flexible pillar making it possible to obtain a support having a longitudinal direction and able to transmit forces between its ends without, or with little, deformation longitudinally and to be easily deformed in a transverse direction.

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TOULOUSE, France

Benjamin Trarieux